Spraying device for aircraft



Patented July 31, 1,951

UNITED STATES PATENTf @oFF-INCE 2,562,524 L; `r

SPRAYING DEVICE Fonv A'I-ReRAFtr f' Clarence W.Y Burnum, Arlington, Tex. Application May-20, 1947, serial No..- 749,389l Y,

i claim. `(ol. 244-136) 'e This invention relates to spraying devices for insecticides, chemicals, or the like, for operation in aircraft in the dissemination of insect poisons to growing crops, and general sanitation spraying operations, and the principal object of the invention resides in the provision of a liquid spray distribution valve adapted to be arranged beneath the wings of an aircraft and capable of being manually operated from the cockpit to effect the discharge of the commodity in desirable volume.

An object of the invention is that of providing apparatus for atomizing liquids and discharging the same in predetermined quantities over dened areas, utilizing the force of air currents through a venturi to produce a jetting action on the diffused liquids and direct them over a wide area in the wake of an aircraft equipped with a suitable number of the apparatus.

A still further object of the invention is manifest in the provision of a chemical spraying device embodying a valve capable of being operated to effectively discharge chemical insecticides and disinfectants in controlled volume and adapted for positive shut-olf action at will whereby spraying operations can be confined to relatively specic boundaries minimizing the possible hazards of overshooting prescribed areas under treatment and discharging the compounds on adjacent properties where such treatment is undesirable.

Broadly, the invention contemplates the provision of a spraying device of simple and economical design by which all types of chemical spraying operations can be performed, such as the chemical treatment of fields, orchards, lakes, and the like, and in which is afforded accurate and effective control of the products with a minimum of eort and in an economical manner.

While the foregoing objects are paramount, other and lesser objects will become manifest as the description proceeds, taken in connection with the appended drawings wherein:

Figure 1 illustrates the invention in partial longitudinal section, taken on lines I-I of Figure 2, showing the same supported beneath the wing of an aircraft, the wing structure being diagram- .matically shown.

Figure 2 is a front elevational view of the in- Vention.

Figure 3 is a detail illustration of the valve, Vshown partially in longitudinal section, and showingdthe form of the discharge openings, therein, an

Figure 4 is a schematic illustration showing a plurality of valves, embodying the invention, arranged on an aircraft shown in outline.

Accordingly, therefore, the inventioncomprises a Venturi tube I6 formed with flared open ends II and I2, its swaged portion I3 .being located a relatively shortA space from the front end II, as shown in Figure l. The member I0 is rigidly secured to mounting 4brackets I4 and I5 by which the -assembly is supported -by the spars I 6 and I1 arranged longitudinally of the wing structures |8 l t, i

It is highly desirable' that .the invention be very rigidly mounted and thus secured against vibration and the force of the air streams passingover the surfaces of the wings I9 in night, and suitable bracing members 20 may be employed between the brackets Ill and I5. The relative spacing of the tubes Ill from the wings I9 should be minimized to afford suitable rigidity although it is not intended that any particular limitations be applied. The tube I0 is properly positioned by slightly inclining the same rearwardly, as in Figure 1.

A valve assembly, illustrated in detail in Figure 3 is arranged in the tube IB and comprises a fluid tube 2| which has a bend a providing a substantially right-angular form, one portion 22 being directed upwardly and through the upper Wall of the tube IIJ in the flared open front end I I thereof, while the opposite portion 23 extends rearwardly in the tube Il), concentrically through.

the venturi I3, land into the longer iiared portion I2 0f the tube i0. A tapered slot 24 is formed in each side of the member 23 and these have their diminishing portions directed toward the forward end I I of the tube i0, as in Figure 3.

A tubular closure member 25, having its outer end 26 closed, slidably embraces the portion 23 of the member 2l and is adapted to move longitudinally thereof and cover the slots 2t. The closure 25 is normally retained against a yieldable seat 2l by a pair of pull springs 28 arranged on opposite sides of the closure 25 and secured at the closed end 26 thereof to a dual bracket member 29 and at their opposite ends to hooks 30 attached to an -annular retainer 3| embracing the seat 2l and securing the latter to the tube 2 I.

It is apparent, therefore, that when the closure 25 is moved away from its seat 21 against the tension of the springs 28 the openings afforded by the slots 24 gradually become larger increasing the ow of liquid therethrough as desired. A

cable 32 is attached to the bracket 29 on each of the valve closures 25 and is arranged over a pulley 33 operatively supported on a bracket 34 3 attached to the upper inner wall o! the flared portion I2 of each of the tubes I0, as illustrated in Figure 1 and is arranged through an aperture 35 and upwardly into the wings I3, over a pulley 36 and is connected to a suitable lever 31 in the cockpit of the plane 38.

It is desirable to provide a lever assembly in which the lever 31 is operated on a segment 39 so that variable fixed adjustments of the valve closure 25 can be accomplished. The movement of the closure 25 is illustrated in dotted' lines in Figure 3.

The valve assemblies are supported in each of the tubes I by the portions 22, ofr the tubes, 2l,

which are arranged through the tops of the tubesl I0 and rigidly secured thereto. The, members,

22 are connected by flexible couplings 40 to fluid conduits 4l which communicate with pipes 42 connected to the reservoir 43 in the fuselage of.

the ship 38 and schematically shown in Figure 4. Any suitable installation at. the; reservoir 43 and connecting conduits 4I` and 42 may be employed', however, to supply the liquid compound to the valves,

In practice, the degree tov which the. slots 24 are opened by the lever 31 will` depend upon the type of sprayingV compound employed in the device and the kind of spraying operations desired. The force of the airv streams passingl into the open front ends Hv olf the tubes: Ill, through the venturi I3 and expanding through the rear end l2, will produce'a very satisfactory diffusing effect upon the liquid. compound and cause it to be discharged in the wake of thev carrier craft 4 in a fog-like mist, capable of being accurately controlled at all times by the operator.

Manifestly, the structure herein shown and described is capable of considerable changes and modifications by persons skilled in the art without departing from the spirit and intent of the invention or the scope of the appended claim.

What is claimed is:

In a chemical spraying device for aircraft, in combination with a chemical tank carried by said aircraftA and discharge conduits therefrom, a Venturi tube arranged about the end of each of said conduits and supported beneath the Wings of said aircraft, a discharge slot on each side of each of said conduits within each of said Venturi tubes, the said slots being tapered toward their inner ends, a sliding closure for each pair of said slots normally closing the same under a spring tension, and a cable for operating each of said closures from the cockpit of said aircraft to uncover said slots against said spring tension from their narrower ends.

CLARENCE W. BURNUM.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 1,580,301 Johnson Apr. 13, 1926 1,957,075 Morgensen May l, 1934 2,378,985 Davis June 26, 1945 

